Battery module configured for use in an electric aircraft

ABSTRACT

A system including a battery module configured for use in an electric aircraft includes at least a battery cell and a battery module casing. The at least a battery cell includes at least a pair of cell tabs and at least a conductor. The battery module casing includes at least a lithiophobic surface with an ejecta barrier and at least a nonlithiphobic surface that is configured to vent the cell ejecta. The battery module casing closely matches the dimensions of the battery cell.

FIELD OF THE INVENTION

The present invention generally relates to the field of electric aircrafts. In particular, the present invention is directed to a battery module for electric aircrafts.

BACKGROUND

Electric aircrafts fold the promise of cleaner transportation without the presently concomitant fossil fuel usage. Electric aircrafts require electric energy storage, for example by the way of battery cells. Battery cells can suffer from thermal runaway. Thermal runaway occurs when a battery cell overheats causing conditions that contribute to further overheating of the battery cell in an uncontrolled positive feedback loop. Conflagration resulting from thermal runaway of a single battery cell is further fueled when thermal runaway progresses to second or third battery cell.

SUMMARY OF THE DISCLOSURE

In an aspect a battery module configured for use in an electric aircraft, the module includes at least a battery cell, the at least a battery cell includes: at least a pair of cell tabs; and at least a conductor; a battery module casing, the casing configured to encompass the at least a battery cell and the at least a conductor, wherein the battery module casing includes: at least a lithiophobic surface including an ejecta barrier; and at least a non-lithiophobic surface, wherein the non-lithiophobic surface is configured to vent the cell ejecta; wherein the module is configured to power an electric aircraft.

In another aspect a method of manufacturing a battery module casing for use in an electric aircraft including: receiving at least a battery cell, the battery cell including: at least a pair of cell tabs; at least a conductor connecting at least a battery cell; receiving at least a battery module casing, the casing including: at least a lithiophobic surface containing an ejecta barrier; at least a non-lithiophobic surface configured to vent an ejecta barrier; placing at least a battery cell in at least a battery module casing; and configuring at least a battery cell to power an electric aircraft.

These and other aspects and features of non-limiting embodiments of the present invention will become apparent to those skilled in the art upon review of the following description of specific non-limiting embodiments of the invention in conjunction with the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

For the purpose of illustrating the invention, the drawings show aspects of one or more embodiments of the invention. However, it should be understood that the present invention is not limited to the precise arrangements and instrumentalities shown in the drawings, wherein:

FIGS. 1A and B are schematic representation of exemplary embodiments of a system for battery module casing shown in front and reverse isometric views;

FIG. 2 is a schematic representation of an exemplary electric vertical take-off and landing vehicle;

FIG. 3 is an illustration of a sensor suite in partial cross-sectional view;

FIG. 4 is a flow diagram of an exemplary method of manufacture for a cell casing configured for use in an electric aircraft;

FIG. 5 is a block diagram of an exemplary embodiment of a machine-learning module; and

FIG. 6 is a block diagram of a computing system that can be used to implement any one or more of the methodologies disclosed herein and any one or more portions thereof.

The drawings are not necessarily to scale and may be illustrated by phantom lines, diagrammatic representations and fragmentary views. In certain instances, details that are not necessary for an understanding of the embodiments or that render other details difficult to perceive may have been omitted.

DETAILED DESCRIPTION

At a high level, aspects of the present disclosure are directed to systems and methods for a battery pack for preventing progression of thermal runaway between modules. In an embodiment, an electric aircraft may include a battery pack for preventing progression of thermal runaway between modules. Some embodiments include methods of manufacture for a battery pack for preventing progression of thermal runaway between modules.

Aspects of the present disclosure can be used to contain ejecta resulting from thermal runaway of a first battery cell, thereby preventing said ejecta from contributing to thermal runaway of a second battery cell. Aspects of the present disclosure can also be used to contain ejecta resulting from heating (e.g., non-thermal runaway conditions) of a first battery cell. This is so, at least in part, because materials ejected from a battery cell prior to thermal runaway may cool and condense on neighboring battery cells; this condensate may then ignite when in presence of increased temperature and/or oxidizer, for example when a nearby battery cell experience thermal runaway.

Aspects of the present disclosure allow for molten ejected materials from a battery cell to be shielded and isolated away from other battery cells. This may prevent ejecta, electrolyte vapors, off-gas, and the like from a first battery cell from influencing thermal conditions of neighboring battery cells or components thereof. Further aspects of the present disclosure may also be used with one or more pouch or prismatic battery cells. In some cases, pouch battery cells may allow for packaging efficiencies in excess of 90% or even 95% compared to other (e.g., can) battery cell packaging systems. Additionally, in some cases, pouch battery cells may be configured to reduce weight of a battery pack. In order to realize the potential offered by electric aircraft batteries must be available that are space and weight efficient and above all safe and reliable. In some embodiments, battery packs according to the present disclosure may be configured for use in electric aircraft and may help to one day fully realize the potential of electric flight. Exemplary embodiments illustrating aspects of the present disclosure are described below in the context of several specific examples.

Referring now to FIGS. 1A and 1B, a system 100 for a battery module casing configured for use in an electric aircraft is shown in front and reverse views. An electric aircraft further includes an electric vertical takeoff and landing aircraft. As used herein, a vertical takeoff and landing (eVTOL) aircraft is one that can hover, take off, and land vertically. An eVTOL, as used herein, is an electrically powered aircraft typically using an energy source, of a plurality of energy sources to power the aircraft. In order to optimize the power and energy necessary to propel the aircraft. eVTOL may be capable of rotor-based cruising flight, rotor-based takeoff, rotor-based landing, fixed-wing cruising flight, airplane-style takeoff, airplane-style landing, and/or any combination thereof. Rotor-based flight, as described herein, is where the aircraft generated lift and propulsion by way of one or more powered rotors coupled with an engine, such as a “quad copter,” multi-rotor helicopter, or other vehicle that maintains its lift primarily using downward thrusting propulsors. Fixed-wing flight, as described herein, is where the aircraft is capable of flight using wings and/or foils that generate life caused by the aircraft's forward airspeed and the shape of the wings and/or foils, such as airplane-style flight.

System 100 includes at least a battery module. Battery module may be configured to provide energy to an electric aircraft via a power supply connection. For the purposes of this disclosure, a “power supply connection” is an electrical and/or physical communication between a battery module and electric aircraft that powers electric aircraft and/or electric aircraft subsystems for operation. In one or more embodiments, system 100 may include a plurality of battery modules. Each battery module may include a battery cell. As used in this disclosure, a “battery cell” is one metallic cathode, one metallic anode, and an electrolyte. For example, and without limitation, battery module may include a plurality of battery cells. Battery cell may include a pouch cell. As used in this disclosure, “pouch cell” is a battery cell or module that includes a pouch. In some cases, a pouch cell may include or be referred to as a prismatic pouch cell, for example when an overall shape of pouch is prismatic. In some cases, a pouch cell may include a pouch which is substantially flexible. Alternatively, or additionally, in some cases, pouch may be substantially rigid. Additional disclosures relating to pouch cells may be found in U.S. Patent Applications entitled “SYSTEM FOR A POUCH CELL CASING CONFIGURED FOR USE IN AN ELECTRIC AIRCRAFT,” having U.S. patent application Ser. No. 17/362,389, filed on Jun. 29, 2021; the entirety of the application is incorporated herein by reference. At least a battery cell may include at least a pair of electrodes. At least a pair of electrodes may include a positive electrode and a negative electrode. Each electrode of at least a pair of electrodes may include an electrically conductive element such that the battery cell includes at least a conductor. Non-limiting exemplary electrically conductive elements include braided wire, solid wire, metallic foil, circuitry, such as printed circuit boards, and the like. System 100 includes at least a pair of cell tabs 108. At least a pair of electrodes may be in electric communication with at least a pair of cell tabs 108. As used herein, a “cell tab” provides connections between the battery cell and the external source that needs to be powered. A cell tab may facilitate the transfer of energy between the battery cell and the external source, such as an electric aircraft. A plurality of conductive tabs welded to the conductor. Conductor may include an electrode. At least a pair of electrodes may also be bonded in electric communication with at least a pair of cell tabs 108 by any known method, including without limitation, brazing, soldering, adhering, engineering fits, electrical connectors, and the like. In some cases, at least a pair of foil tabs may include a cathode and an anode. In some cases, an exemplary cathode may include a lithium-based substance, such as lithium-metal oxide, bonded to an aluminum foil tab. In some cases, an exemplary anode may include a carbon-based substance, such as graphite, bonded to a copper tab. At least a conductor within a battery cell is electrically connected to an electric bus. For the purposes of this disclosure, a “bus bar or bus” is an electrically conductive pathway connecting at least a component in a system configured to convey electrical energy between components. The bus bar may include one or more electrically conductive pathways configured to transfer electrical energy across the pathways to convey electrical energy from one component to one or more other components. Bus bar may include, without limitation, one or more metallic strips and/or bars. Bus bar may include a ring bus. For the purpose of this disclosure, a “ring bus” is a bus element wherein circuit breakers are connected to form a ring with isolators on both sides of each circuit breaker. Ring bus may include component configured to isolate a fault by tripping two circuit breakers while all other circuits remain in service. Bus bar may be disposed in or on a switchgear, panel board, busway enclosure, a plurality of energy storage elements, any portion of electric aircraft, a plurality of propulsors, or a combination thereof. A bus bar may also be used to connect high voltage equipment at electrical switchyards, and low voltage equipment in plurality of energy storage element. Bus bar may be uninsulated; bus bar may have sufficient stiffness to be supported in air by insulated pillars. These features allow sufficient cooling of the conductors, and the ability to tap in at various points without creating a new joint. A bus bar may include material composition and cross-sectional size configured to conduct electricity where the size and material determine the maximum amount of current that can be safely carried. A bus bar may be produced in a plurality of shapes including flat strips, solid bars, rods, or a combination thereof. A bus bar may be composed of copper, brass, aluminum as solid or hollow tubes, in embodiments. A bus bar may include flexible buses wherein thin conductive layers are sandwiched together; such an arrangement may include a structural frame and/or cabinet configured to provide rigidity to bus bar. A bus bar may include distribution boards configured to split the electrical supply into separate circuits at one location. Busways, or bus ducts, are long busbars with a protective cover. Rather than branching from the main supply at one location, they allow new circuits to branch off anywhere along the route of the busway. Bus bar may either be supported on insulators, or else insulation may completely surround it. Bus bars are protected from accidental contact either by an enclosure or by design configured to remove it from reach. Bus bar may be connected to each other and to electrical apparatus by bolted, clamped, or welded connections. Joints between high-current bus bar sections have precisely machined matching surfaces that are silver-plated to reduce the contact resistance. Electrical bus may refer to power busses, audio busses, video busses, computing address busses, and/or data busses.

With continued reference to FIGS. 1A and 1B, battery cell may include Li ion batteries which may include NCA, NMC, Lithium iron phosphate (LiFePO4) and Lithium Manganese Oxide (LMO) batteries, which may be mixed with another cathode chemistry to provide more specific power if the application requires Li metal batteries, which have a lithium metal anode that provides high power on demand, Li ion batteries that have a silicon, tin nanocrystals, graphite, graphene or titanate anode, or the like. Batteries and/or battery modules may include without limitation batteries using nickel-based chemistries such as nickel cadmium or nickel metal hydride, batteries using lithium-ion battery chemistries such as a nickel cobalt aluminum (NCA), nickel manganese cobalt (NMC), lithium iron phosphate (LiFePO4), lithium cobalt oxide (LCO), and/or lithium manganese oxide (LMO), batteries using lithium polymer technology, metal-air batteries. Battery cell may include lead-based batteries such as without limitation lead acid batteries and lead carbon batteries. Battery cell may include lithium sulfur batteries, magnesium ion batteries, and/or sodium ion batteries. Batteries may include solid state batteries or supercapacitors or another suitable energy source. Batteries may be primary or secondary or a combination of both. Additional disclosure related to batteries and battery modules may be found in co-owned U.S. Patent Applications entitled “SYSTEM AND METHOD FOR HIGH ENERGY DENSITY BATTERY MODULE” and “SYSTEMS AND METHODS FOR RESTRICTING POWER TO A LOAD TO PREVENT ENGAGING CIRCUIT PROTECTION DEVICE FOR AN AIRCRAFT,” having U.S. patent application Ser. Nos. 16/948,140 and 16/590,496 respectively; the entirety of both applications are incorporated herein by reference. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various devices of components that may be used as a battery module.

With continued reference to FIGS. 1A and 1B, at least a battery cell may include a pouch 116. Pouch 116 is configured to substantially encompass at least a pair of cell tabs 108, battery cell 104, and includes at least a first side 120. In some cases, pouch 116 may include a polymer, such as without limitation polyethylene, acrylic, polyester, and the like. In some case, pouch 116 may be coated with one or more coatings. For example, in some cases, pouch may have an outer surface coated with a metalizing coating, such as an aluminum or nickel containing coating. In some cases, pouch coating be configured to electrically ground and/or isolate pouch, increase pouches impermeability, increase pouches resistance to high temperatures, increases pouches thermal resistance (insulation), and the like. An electrolyte may be located within pouch 116. In some cases, an electrolyte may include a liquid, a solid, a gel, a paste, and/or a polymer. An electrolyte may wet or contact one or both of at least a pair of cell tabs 108. At least a pair of cell tabs 108 of a battery cell may be configured to be electrically connected to one or more other pairs of cell tabs similar to or the same as the at least a pair of cell tabs 108. At least a battery cell may be disposed in columns, rows, grids, stacks, layups, or other arrangements. At least a battery cell may be mechanically, electrically, and otherwise connected to proximate battery cells in series, parallel, or a combination thereof.

With continued reference to FIGS. 1A and 1B, system 100 includes a battery module casing 124. Battery module casing 124 is configured to encompass at least a battery module, including at least a battery cell. Battery module casing is configured to closely match the dimensions of at least a battery module. For example and without limitation, a box shaped battery module may be encompassed by a box shaped battery module casing. At least a battery cell is connected to the battery module casing by a bonding. Bondings may include fasteners, adhesives, weld, solder, braze, and the like. Battery module casing may contain intermediate surfaces. Intermediate surfaces may be used to position the battery module within the casing using compliant forces. For instance, a compliant intermediate layer may be disposed between the casing and the battery module such that there is an intermediate layer on opposing sides of the battery module. Intermediate surfaces may be comprised of the same material as the surfaces of the battery module casing. Materials for such are discussed below. Intermediate surfaces may also be comprised of thermally conductive materials such as aluminum, copper, or the like such that the surface may be used to transfer heat between the battery module and the battery module casing. Alternatively, intermediate surfaces may be comprised of electrically insulating materials such as rubber, glass, or the like such that the surface may be used to insulate the battery module from the casing. Intermediate surfaces may be selected to perform a number of functions, not limited to, providing compressive forces, providing dampening, or providing compliance between the casing and the battery module.

Still referring to FIGS. 1A and 1B, intermediate surfaces may comprise an insulator layer. As used in this disclosure, an “insulator layer” is an electrically insulating material that is substantially permeable to battery ions, such as without limitation lithium ions. In some cases, insulator layer may be referred to as a separator layer or simply separator. In some cases, insulator layer may be included and configured to prevent electrical communication directly between at least a pair of cell tabs 108 (e.g., cathode and anode). In some cases, an insulator layer may be configured to allow for a flow ions across it. An insulator layer may consist of a polymer, for example polyolefin (PO). An insulator layer may include pours which are configured to allow for passage of ions, for example lithium ions. In some cases, pours of a PO insulator layer may have a width no greater than 100 μm, 10 μm, 1 μm, or 0.1 μm. In some cases, a PO insulator layer may have a thickness within a range of 1-100 μm, or 10-30 μm.

Still referring to FIGS. 1A and 1B, battery module casing 124 includes at least a lithiophobic surface, wherein the lithiophobic surface is configured to contain an ejecta barrier. As used in this disclosure, a “lithiophobic material” is any material that is configured to repel lithium-based compounds. For example, some materials may include, without limitation, graphene, graphite, carbon fiber, and the like. Battery module casing 124 may include metals, composites and the like. Battery module casing 124 may be manufactured in a plurality of methods including welding, casting, molding, forging, and the like. For example, in some instances battery module casing 124 may be substantially impermeable to ejecta from battery at least a battery cell 104. In some cases, an ejecta barrier be configured to absorb and/or repel lithium-based compounds. In some cases, an ejecta barrier may include a lithiophilic metal coating, such as silver or gold. In some cases, an ejecta barrier may be flexible and/or rigid. In some cases, an ejecta barrier may include a sheet, a film, a foil, or the like. Alternatively or additionally, in some cases, battery module casing 124 may include rigid and/or structural elements, for instance which are solid. In some cases, an ejecta barrier may be further configured to structurally support at least a battery cell 104. For example in some cases, at least a battery cell 104 may be mounted to a rigid an ejecta barrier.

With continued reference to FIGS. 1A and 1B, at least a lithiophobic surface is configured to prevent ejecta from traveling outside the battery module casing. First face 128 may be at least a lithiophobic surface. Ejecta barrier may be used to block, arrest, capture, catch, deflect, contain, otherwise direct one or more objects ejected from the at least a battery cell 104. As used in this disclosure, an “ejecta barrier” is any material or structure that is configured to substantially block, contain, or otherwise prevent passage of ejecta. As used in this disclosure, “ejecta” is any material that has been ejected, for example from a battery cell. In some cases, ejecta may be ejected during thermal runaway of a battery cell. In some cases, ejecta may include hot matter, which if left uncontained could transfer heat to other, e.g., neighboring, battery cells. At least a lithiophobic surface is configured to transfer heat from at least the at least a battery cell to the battery module casing. By preventing hot ejecta from reaching battery cells, battery module casing 124 may aid in preventing progression of thermal runaway between battery cells within a battery pack in which the herein system 100 is disposed. In some cases, ejecta may include combustible materials, which if left uncontained could settle upon other, e.g., neighboring, battery cells. Combustible materials once combustion conditions are met may combust generating an exothermic reaction, which can induce thermal runaway on nearby battery cells. Combustion conditions can include presence of oxygen, fuel, spark, flash point, fire point, and/or autoignition temperature. Alternatively or additionally, in some cases, eject may be ejected without thermal runaway of a battery cell. In some cases, ejecta may include lithium-based compounds. Alternatively or additionally, ejecta may include carbon-based compounds, such as without limitation carbonate esters. Ejecta may include matter in any phase or form, including solid, liquid, gas, vapor, and the like. In some cases, ejecta may undergo a phase change, for example ejecta may be vaporous as it is initially being ejected and then cool and condense into a solid or liquid after ejection.

With continued reference to FIGS. 1A and 1B, system 100 includes at least an opening 136 disposed on and through a portion of first face 128. At least an opening 136 may include a polygonal cut-through of first face 128 such that there is a path from one side of first face 128 to the opposite and opposing side of first face 128 through at least an opening 136. At least an opening 136 may include any polygonal shape in substantially flat first face 128 such as a square, rectangle, circle, oval, triangle and in any pattern or number thereof. At least an opening 136 may include slots, grating, slits, patterns of holes, grids, ranks, columns, rows, or other arrangements of at least an opening 136. At least an opening 136 may be punched, sawn, cast, molded, forged, drilled, milled, additively manufactured (various forms of three-dimensional (3D) printing), electrical discharged machined (EDM), machined, turned, or any other suitable method of manufacture. At least an opening 136 may be configured to reduce weight of battery module casing 124. At least an opening 136 may be disposed on and through a portion of battery module casing 124 configured to not be impacted in the event ejecta strikes battery module casing 124. At least an opening 136 may include duck bills, teeth, edges, or other mechanical features configured to arrest liquid ejecta disposed on the edges of at least an opening 136.

With continued reference to FIGS. 1A and 1B, battery module casing is composed of at least one face of non-lithiophobic material. Second face 132 may be the non-lithiophobic surface. Second face 132 is configured to vent the cell ejecta. As used in this disclosure, “non-lithiophobic surface” includes any non-conducting material that is configured to repel lithium-based compounds. For example, some materials may include vermiculite, titanium, polymers, and the like. Polymers may include PEEK, Ultem, etc.

With continued reference to FIGS. 1A and 1B, system 100 may include at least a vent 140 as previously disclosed. In some cases, at least a vent 140 may be configured to vent ejecta from at least a battery cell 104. In some cases, at least a vent 140 may be configured to vent ejecta along a flow path. Flow path 144 may substantially exclude components within system 100, for example fluids flowing along the flow path 144 may be cordoned away from contact with components disposed near the flow path. For example, flow path 144 may be configured to not intersect with any surface of second battery cell. A flow path 144 may include any channel, tube, hose, conduit, or the like suitable for facilitating fluidic communication, for example with a at least a battery cell 104. In some cases, the flow path 144 may include a check valve. As used in this disclosure, a “check valve” is a valve that permits flow of a fluid only in certain, for example one, direction. In some cases, the check valve may be configured to allow flow of fluids substantially only away from battery at least a battery cell 104, while preventing back flow of vented fluid to the battery at least a battery cell 104. In some cases, the check valve may include a duckbill check valve. In some cases, a duckbill check valve may have lips which are substantially in a shape of a duckbill. Lips may be configured to open to allow forward flow (out of the lips), while remaining normally closed to prevent backflow (into the lips). In some cases, duckbill lips may be configured to automatically close (remain normally closed), for example with use of a compliant element, such as without limitation an elastomeric material, a spring, and the like. In some embodiments, vent 140 may include a mushroom poppet valve. In some cases, a mushroom poppet valve may include a mushroom shaped poppet. Mushroom shaped poppet may seal against a sealing element, for example a ring about an underside of a cap of the mushroom shaped poppet. In some cases, mushroom poppet valve may be loaded against sealing element, for example by way of a compliant element, such as a spring. According to some embodiments, vent 140 may have a vacuum applied to aid in venting of cell ejecta. Vacuum pressure differential may range from 0.1″ Hg to 36″ Hg.

With continued reference to FIGS. 1A and 1B, the battery module includes a sensor suite. In some cases, a sensor in a sensor suite may be configured to sense battery pack data and transmit battery pack data to a data storage system, for example as described below in reference to FIGS. 4-5 . Additionally or alternatively, system 100 is configured to power an electric aircraft. An electric aircraft may contain a propulsor component, wherein a propulsor component is described below in reference to FIG. 2 .

Referring now to FIG. 2 , an exemplary embodiment of an aircraft 200 is illustrated. Aircraft 200 may include an electrically powered aircraft. In some embodiments, electrically powered aircraft may be an electric vertical takeoff and landing (eVTOL) aircraft. Electric aircraft may be capable of rotor-based cruising flight, rotor-based takeoff, rotor-based landing, fixed-wing cruising flight, airplane-style takeoff, airplane-style landing, and/or any combination thereof. “Rotor-based flight,” as described in this disclosure, is where the aircraft generated lift and propulsion by way of one or more powered rotors coupled with an engine, such as a quadcopter, multi-rotor helicopter, or other vehicle that maintains its lift primarily using downward thrusting propulsors. “Fixed-wing flight,” as described in this disclosure, is where the aircraft is capable of flight using wings and/or foils that generate lift caused by the aircraft's forward airspeed and the shape of the wings and/or foils, such as airplane-style flight.

Still referring to FIG. 2 , aircraft 200 may include a fuselage 204. As used in this disclosure a “fuselage” is the main body of an aircraft, or in other words, the entirety of the aircraft except for the cockpit, nose, wings, empennage, nacelles, any and all control surfaces, and generally contains an aircraft's payload. Fuselage 204 may comprise structural elements that physically support the shape and structure of an aircraft. Structural elements may take a plurality of forms, alone or in combination with other types. Structural elements may vary depending on the construction type of aircraft and specifically, the fuselage. Fuselage 204 may comprise a truss structure. A truss structure may be used with a lightweight aircraft and may include welded aluminum tube trusses. A truss, as used herein, is an assembly of beams that create a rigid structure, often in combinations of triangles to create three-dimensional shapes. A truss structure may alternatively comprise titanium construction in place of aluminum tubes, or a combination thereof. In some embodiments, structural elements may comprise aluminum tubes and/or titanium beams. In an embodiment, and without limitation, structural elements may include an aircraft skin. Aircraft skin may be layered over the body shape constructed by trusses. Aircraft skin may comprise a plurality of materials such as aluminum, fiberglass, and/or carbon fiber, the latter of which will be addressed in greater detail later in this paper.

Still referring to FIG. 2 , aircraft 200 may include a plurality of actuators 208. In an embodiment, actuator 108 may be mechanically coupled to an aircraft. As used herein, a person of ordinary skill in the art would understand “mechanically coupled” to mean that at least a portion of a device, component, or circuit is connected to at least a portion of the aircraft via a mechanical coupling. Said mechanical coupling can include, for example, rigid coupling, such as beam coupling, bellows coupling, bushed pin coupling, constant velocity, split-muff coupling, diaphragm coupling, disc coupling, donut coupling, elastic coupling, flexible coupling, fluid coupling, gear coupling, grid coupling, Hirth joints, hydrodynamic coupling, jaw coupling, magnetic coupling, Oldham coupling, sleeve coupling, tapered shaft lock, twin spring coupling, rag joint coupling, universal joints, or any combination thereof. As used in this disclosure an “aircraft” is vehicle that may fly. As a non-limiting example, aircraft may include airplanes, helicopters, airships, blimps, gliders, paramotors, and the like thereof. In an embodiment, mechanical coupling may be used to connect the ends of adjacent parts and/or objects of an electric aircraft. Further, in an embodiment, mechanical coupling may be used to join two pieces of rotating electric aircraft components.

With continued reference to FIG. 2 , a plurality of actuators 208 may be configured to produce a torque. As used in this disclosure a “torque” is a measure of force that causes an object to rotate about an axis in a direction. For example, and without limitation, torque may rotate an aileron and/or rudder to generate a force that may adjust and/or affect altitude, airspeed velocity, groundspeed velocity, direction during flight, and/or thrust. For example, plurality of actuators 208 may include a component used to produce a torque that affects aircrafts' roll and pitch, such as without limitation one or more ailerons. An “aileron,” as used in this disclosure, is a hinged surface which form part of the trailing edge of a wing in a fixed wing aircraft, and which may be moved via mechanical means such as without limitation servomotors, mechanical linkages, or the like. As a further example, plurality of actuators 208 may include a rudder, which may include, without limitation, a segmented rudder that produces a torque about a vertical axis. Additionally or alternatively, plurality of actuators 208 may include other flight control surfaces such as propulsors, rotating flight controls, or any other structural features which can adjust movement of aircraft 200. Plurality of actuators 208 may include one or more rotors, turbines, ducted fans, paddle wheels, and/or other components configured to propel a vehicle through a fluid medium including, but not limited to air.

Still referring to FIG. 2 , plurality of actuators 208 may include at least a propulsor component. As used in this disclosure a “propulsor component” is a component and/or device used to propel a craft by exerting force on a fluid medium, which may include a gaseous medium such as air or a liquid medium such as water. In an embodiment, when a propulsor twists and pulls air behind it, it may, at the same time, push an aircraft forward with an amount of force and/or thrust. More air pulled behind an aircraft results in greater thrust with which the aircraft is pushed forward. Propulsor component may include any device or component that consumes electrical power on demand to propel an electric aircraft in a direction or other vehicle while on ground or in-flight. In an embodiment, propulsor component may include a puller component. As used in this disclosure a “puller component” is a component that pulls and/or tows an aircraft through a medium. As a non-limiting example, puller component may include a flight component such as a puller propeller, a puller motor, a puller propulsor, and the like. Additionally, or alternatively, puller component may include a plurality of puller flight components. In another embodiment, propulsor component may include a pusher component. As used in this disclosure a “pusher component” is a component that pushes and/or thrusts an aircraft through a medium. As a non-limiting example, pusher component may include a pusher component such as a pusher propeller, a pusher motor, a pusher propulsor, and the like. Additionally, or alternatively, pusher flight component may include a plurality of pusher flight components.

In another embodiment, and still referring to FIG. 2 , propulsor may include a propeller, a blade, or any combination of the two. A propeller may function to convert rotary motion from an engine or other power source into a swirling slipstream which may push the propeller forwards or backwards. Propulsor may include a rotating power-driven hub, to which several radial airfoil-section blades may be attached, such that an entire whole assembly rotates about a longitudinal axis. As a non-limiting example, blade pitch of propellers may be fixed at a fixed angle, manually variable to a few set positions, automatically variable (e.g. a “constant-speed” type), and/or any combination thereof as described further in this disclosure. As used in this disclosure a “fixed angle” is an angle that is secured and/or substantially unmovable from an attachment point. For example, and without limitation, a fixed angle may be an angle of 2.2° inward and/or 1.7 forward. As a further non-limiting example, a fixed angle may be an angle of 2.6° outward and/or 2.7° backward. In an embodiment, propellers for an aircraft may be designed to be fixed to their hub at an angle similar to the thread on a screw makes an angle to the shaft; this angle may be referred to as a pitch or pitch angle which may determine a speed of forward movement as the blade rotates. Additionally or alternatively, propulsor component may be configured having a variable pitch angle. As used in this disclosure a “variable pitch angle” is an angle that may be moved and/or rotated. For example, and without limitation, propulsor component may be angled at a first angle of 2.3° inward, wherein propulsor component may be rotated and/or shifted to a second angle of 1.7° outward.

Still referring to FIG. 2 , propulsor may include a thrust element which may be integrated into the propulsor. Thrust element may include, without limitation, a device using moving or rotating foils, such as one or more rotors, an airscrew or propeller, a set of airscrews or propellers such as contra-rotating propellers, a moving or flapping wing, or the like. Further, a thrust element, for example, can include without limitation a marine propeller or screw, an impeller, a turbine, a pump-jet, a paddle or paddle-based device, or the like.

With continued reference to FIG. 2 , plurality of actuators 208 may include power sources, control links to one or more elements, fuses, and/or mechanical couplings used to drive and/or control any other flight component. Plurality of actuators 208 may include a motor that operates to move one or more flight control components and/or one or more control surfaces, to drive one or more propulsors, or the like. A motor may be driven by direct current (DC) electric power and may include, without limitation, brushless DC electric motors, switched reluctance motors, induction motors, or any combination thereof. Alternatively or additionally, a motor may be driven by an inverter. A motor may also include electronic speed controllers, inverters, or other components for regulating motor speed, rotation direction, and/or dynamic braking.

Still referring to FIG. 2 , plurality of actuators 208 may include an energy source. An energy source may include, for example, a generator, a photovoltaic device, a fuel cell such as a hydrogen fuel cell, direct methanol fuel cell, and/or solid oxide fuel cell, an electric energy storage device (e.g. a capacitor, an inductor, and/or a battery). An energy source may also include a battery cell, or a plurality of battery cells connected in series into a module and each module connected in series or in parallel with other modules. Energy source may include a battery pack, for example as described in reference to FIGS. 1A and 1B. Configuration of an energy source containing connected modules may be designed to meet an energy or power requirement and may be designed to fit within a designated footprint in an electric aircraft in which system may be incorporated.

In an embodiment, and still referring to FIG. 2 , an energy source may be used to provide a steady supply of electrical power to a load over a flight by an electric aircraft 200. For example, energy source may be capable of providing sufficient power for “cruising” and other relatively low-energy phases of flight. An energy source may also be capable of providing electrical power for some higher-power phases of flight as well, particularly when the energy source is at a high SOC, as may be the case for instance during takeoff. In an embodiment, energy source may include an emergency power unit which may be capable of providing sufficient electrical power for auxiliary loads including without limitation, lighting, navigation, communications, de-icing, steering or other systems requiring power or energy. Further, energy source may be capable of providing sufficient power for controlled descent and landing protocols, including, without limitation, hovering descent or runway landing. As used herein the energy source may have high power density where electrical power an energy source can usefully produce per unit of volume and/or mass is relatively high. As used in this disclosure, “electrical power” is a rate of electrical energy per unit time. An energy source may include a device for which power that may be produced per unit of volume and/or mass has been optimized, for instance at an expense of maximal total specific energy density or power capacity. Non-limiting examples of items that may be used as at least an energy source include batteries used for starting applications including Li ion batteries which may include NCA, NMC, Lithium iron phosphate (LiFePO4) and Lithium Manganese Oxide (LMO) batteries, which may be mixed with another cathode chemistry to provide more specific power if the application requires Li metal batteries, which have a lithium metal anode that provides high power on demand, Li ion batteries that have a silicon or titanite anode, energy source may be used, in an embodiment, to provide electrical power to an electric aircraft or drone, such as an electric aircraft vehicle, during moments requiring high rates of power output, including without limitation takeoff, landing, thermal de-icing and situations requiring greater power output for reasons of stability, such as high turbulence situations, as described in further detail below. A battery may include, without limitation a battery using nickel based chemistries such as nickel cadmium or nickel metal hydride, a battery using lithium ion battery chemistries such as a nickel cobalt aluminum (NCA), nickel manganese cobalt (NMC), lithium iron phosphate (LiFePO4), lithium cobalt oxide (LCO), and/or lithium manganese oxide (LMO), a battery using lithium polymer technology, lead-based batteries such as without limitation lead acid batteries, metal-air batteries, or any other suitable battery. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various devices of components that may be used as an energy source.

Still referring to FIG. 2 , an energy source may include a plurality of energy sources, referred to herein as a module of energy sources. Module may include batteries connected in parallel or in series or a plurality of modules connected either in series or in parallel designed to satisfy both power and energy requirements. Connecting batteries in series may increase a potential of at least an energy source which may provide more power on demand. High potential batteries may require cell matching when high peak load is needed. As more cells are connected in strings, there may exist a possibility of one cell failing which may increase resistance in module and reduce overall power output as voltage of the module may decrease as a result of that failing cell. Connecting batteries in parallel may increase total current capacity by decreasing total resistance, and it also may increase overall amp-hour capacity. Overall energy and power outputs of at least an energy source may be based on individual battery cell performance or an extrapolation based on a measurement of at least an electrical parameter. In an embodiment where energy source includes a plurality of battery cells, overall power output capacity may be dependent on electrical parameters of each individual cell. If one cell experiences high self-discharge during demand, power drawn from at least an energy source may be decreased to avoid damage to a weakest cell. Energy source may further include, without limitation, wiring, conduit, housing, cooling system and battery management system. Persons skilled in the art will be aware, after reviewing the entirety of this disclosure, of many different components of an energy source. Exemplary energy sources are disclosed in detail in U.S. patent application Ser. Nos. 16/948,157 and 16/048,140 both entitled “SYSTEM AND METHOD FOR HIGH ENERGY DENSITY BATTERY MODULE” by S. Donovan et al., which are incorporated in their entirety herein by reference.

Still referring to FIG. 2 , according to some embodiments, an energy source may include an emergency power unit (EPU) (i.e., auxiliary power unit). As used in this disclosure an “emergency power unit” is an energy source as described herein that is configured to power an essential system for a critical function in an emergency, for instance without limitation when another energy source has failed, is depleted, or is otherwise unavailable. Exemplary non-limiting essential systems include navigation systems, such as MFD, GPS, VOR receiver or directional gyro, and other essential flight components, such as propulsors.

Still referring to FIG. 2 , another exemplary actuator may include landing gear. Landing gear may be used for take-off and/or landing/Landing gear may be used to contact ground while aircraft 200 is not in flight. Exemplary landing gear is disclosed in detail in U.S. patent application Ser. No. 17/196,719 entitled “SYSTEM FOR ROLLING LANDING GEAR” by R. Griffin et al., which is incorporated in its entirety herein by reference.

Still referring to FIG. 2 , aircraft 200 may include a pilot control 212, including without limitation, a hover control, a thrust control, an inceptor stick, a cyclic, and/or a collective control. As used in this disclosure a “collective control” is a mechanical control of an aircraft that allows a pilot to adjust and/or control the pitch angle of the plurality of actuators 208. For example, and without limitation, collective control may alter and/or adjust the pitch angle of all of the main rotor blades collectively. For example, and without limitation pilot control 212 may include a yoke control. As used in this disclosure a “yoke control” is a mechanical control of an aircraft to control the pitch and/or roll. For example, and without limitation, yoke control may alter and/or adjust the roll angle of aircraft 200 as a function of controlling and/or maneuvering ailerons. In an embodiment, pilot control 212 may include one or more footbrakes, control sticks, pedals, throttle levels, and the like thereof. In another embodiment, and without limitation, pilot control 212 may be configured to control a principal axis of the aircraft. As used in this disclosure a “principal axis” is an axis in a body representing one three dimensional orientations. For example, and without limitation, principal axis or more yaw, pitch, and/or roll axis. Principal axis may include a yaw axis. As used in this disclosure a “yaw axis” is an axis that is directed towards the bottom of the aircraft, perpendicular to the wings. For example, and without limitation, a positive yawing motion may include adjusting and/or shifting the nose of aircraft 200 to the right. Principal axis may include a pitch axis. As used in this disclosure a “pitch axis” is an axis that is directed towards the right laterally extending wing of the aircraft. For example, and without limitation, a positive pitching motion may include adjusting and/or shifting the nose of aircraft 200 upwards. Principal axis may include a roll axis. As used in this disclosure a “roll axis” is an axis that is directed longitudinally towards the nose of the aircraft, parallel to the fuselage. For example, and without limitation, a positive rolling motion may include lifting the left and lowering the right wing concurrently.

Still referring to FIG. 2 , pilot control 212 may be configured to modify a variable pitch angle. For example, and without limitation, pilot control 212 may adjust one or more angles of attack of a propeller. As used in this disclosure an “angle of attack” is an angle between the chord of the propeller and the relative wind. For example, and without limitation angle of attack may include a propeller blade angled 2.2°. In an embodiment, pilot control 212 may modify the variable pitch angle from a first angle of 2.71° to a second angle of 2.82°. Additionally or alternatively, pilot control 212 may be configured to translate a pilot desired torque for flight component. For example, and without limitation, pilot control 212 may translate that a pilot's desired torque for a propeller be 160 lb. ft. of torque. As a further non-limiting example, pilot control 212 may introduce a pilot's desired torque for a propulsor to be 290 lb. ft. of torque. Additional disclosure related to pilot control 212 may be found in U.S. patent application Ser. Nos. 17/001,845 and 16/929,206 both of which are entitled “A HOVER AND THRUST CONTROL ASSEMBLY FOR DUAL-MODE AIRCRAFT” by C. Spiegel et al., which are incorporated in their entirety herein by reference.

Still referring to FIG. 2 , aircraft 200 may include a loading system. A loading system may include a system configured to load an aircraft of either cargo or personnel. For instance, some examples of loading systems may include a swing nose, which is configured to swing the nose of aircraft 200 of the way thereby allowing direct access to a cargo bay located behind the nose. A notable example of a swing nose aircraft is Boeing 647. Additional disclosure related to loading systems can be found in U.S. patent application Ser. No. 17/137,594 entitled “SYSTEM AND METHOD FOR LOADING AND SECURING PAYLOAD IN AN AIRCRAFT” by R. Griffin et al., entirety of which in incorporated herein by reference.

Still referring to FIG. 2 , aircraft 200 may include a sensor 216. Sensor 216 may be configured to sense a characteristic of pilot control 212. Sensor may be a device, module, and/or subsystem, utilizing any hardware, software, and/or any combination thereof to sense a characteristic and/or changes thereof, in an instant environment, for instance without limitation a pilot control 212, which the sensor is proximal to or otherwise in a sensed communication with, and transmit information associated with the characteristic, for instance without limitation digitized data. Sensor 216 may be mechanically and/or communicatively coupled to aircraft 200, including, for instance, to at least a pilot control 212. Sensor 216 may be configured to sense a characteristic associated with at least a pilot control 212. An environmental sensor may include without limitation one or more sensors used to detect ambient temperature, barometric pressure, and/or air velocity, one or more motion sensors which may include without limitation gyroscopes, accelerometers, inertial measurement unit (IMU), and/or magnetic sensors, one or more humidity sensors, one or more oxygen sensors, or the like. Additionally or alternatively, sensor 216 may include at least a geospatial sensor. Sensor 216 may be located inside an aircraft; and/or be included in and/or attached to at least a portion of the aircraft. Sensor may include one or more proximity sensors, displacement sensors, vibration sensors, and the like thereof. Sensor may be used to monitor the status of aircraft 200 for both critical and non-critical functions. Sensor may be incorporated into vehicle or aircraft or be remote.

Still referring to FIG. 2 , in some embodiments, sensor 216 may be configured to sense a characteristic associated with any pilot control described in this disclosure. Non-limiting examples of a sensor 216 may include an inertial measurement unit (IMU), an accelerometer, a gyroscope, a proximity sensor, a pressure sensor, a light sensor, a pitot tube, an air speed sensor, a position sensor, a speed sensor, a switch, a thermometer, a strain gauge, an acoustic sensor, and an electrical sensor. In some cases, sensor 216 may sense a characteristic as an analog measurement, for instance, yielding a continuously variable electrical potential indicative of the sensed characteristic. In these cases, sensor 216 may additionally comprise an analog to digital converter (ADC) as well as any additionally circuitry, such as without limitation a Whetstone bridge, an amplifier, a filter, and the like. For instance, in some cases, sensor 216 may comprise a strain gage configured to determine loading of one or flight components, for instance landing gear. Strain gage may be included within a circuit comprising a Whetstone bridge, an amplified, and a bandpass filter to provide an analog strain measurement signal having a high signal to noise ratio, which characterizes strain on a landing gear member. An ADC may then digitize analog signal produces a digital signal that can then be transmitted other systems within aircraft 200, for instance without limitation a computing system, a pilot display, and a memory component. Alternatively or additionally, sensor 216 may sense a characteristic of a pilot control 212 digitally. For instance in some embodiments, sensor 216 may sense a characteristic through a digital means or digitize a sensed signal natively. In some cases, for example, sensor 216 may include a rotational encoder and be configured to sense a rotational position of a pilot control; in this case, the rotational encoder digitally may sense rotational “clicks” by any known method, such as without limitation magnetically, optically, and the like.

Still referring to FIG. 2 , electric aircraft may include flight controller 220 which may be the same as or similar to any flight controller as described herein. Electric aircraft 200 may include at least a motor 224, which may be mounted on a structural feature of the aircraft. Design of motor 224 may enable it to be installed external to structural member (such as a boom, nacelle, or fuselage) for easy maintenance access and to minimize accessibility requirements for the structure; this may improve structural efficiency by requiring fewer large holes in the mounting area. In some embodiments, motor 224 may include two main holes in top and bottom of mounting area to access bearing cartridge. Further, a structural feature may include a component of electric aircraft 200. For example, and without limitation structural feature may be any portion of a vehicle incorporating motor 224, including any vehicle as described in this disclosure. As a further non-limiting example, a structural feature may include without limitation a wing, a spar, an outrigger, a fuselage, or any portion thereof; persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of many possible features that may function as at least a structural feature. At least a structural feature may be constructed of any suitable material or combination of materials, including without limitation metal such as aluminum, titanium, steel, or the like, polymer materials or composites, fiberglass, carbon fiber, wood, or any other suitable material. As a non-limiting example, at least a structural feature may be constructed from additively manufactured polymer material with a carbon fiber exterior; aluminum parts or other elements may be enclosed for structural strength, or for purposes of supporting, for instance, vibration, torque or shear stresses imposed by at least propulsor 208. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various materials, combinations of materials, and/or constructions techniques.

Still referring to FIG. 2 , electric aircraft 200 may include a vertical takeoff and landing aircraft (eVTOL). As used herein, a vertical take-off and landing (eVTOL) aircraft is one that can hover, take off, and land vertically. An eVTOL, as used herein, is an electrically powered aircraft typically using an energy source, of a plurality of energy sources to power the aircraft. In order to optimize the power and energy necessary to propel the aircraft. eVTOL may be capable of rotor-based cruising flight, rotor-based takeoff, rotor-based landing, fixed-wing cruising flight, airplane-style takeoff, airplane-style landing, and/or any combination thereof. Rotor-based flight, as described herein, is where the aircraft generated lift and propulsion by way of one or more powered rotors coupled with an engine, such as a “quad copter,” multi-rotor helicopter, or other vehicle that maintains its lift primarily using downward thrusting propulsors. Fixed-wing flight, as described herein, is where the aircraft is capable of flight using wings and/or foils that generate life caused by the aircraft's forward airspeed and the shape of the wings and/or foils, such as airplane-style flight.

With continued reference to FIG. 2 , a number of aerodynamic forces may act upon the electric aircraft 200 during flight. Forces acting on electric aircraft 200 during flight may include, without limitation, thrust, the forward force produced by the rotating element of the electric aircraft 900 and acts parallel to the longitudinal axis. Another force acting upon electric aircraft 200 may be, without limitation, drag, which may be defined as a rearward retarding force which is caused by disruption of airflow by any protruding surface of the electric aircraft 200 such as, without limitation, the wing, rotor, and fuselage. Drag may oppose thrust and acts rearward parallel to the relative wind. A further force acting upon electric aircraft 200 may include, without limitation, weight, which may include a combined load of the electric aircraft 200 itself, crew, baggage, and/or fuel. Weight may pull electric aircraft 200 downward due to the force of gravity. An additional force acting on electric aircraft 200 may include, without limitation, lift, which may act to oppose the downward force of weight and may be produced by the dynamic effect of air acting on the airfoil and/or downward thrust from the propulsor 208 of the electric aircraft. Lift generated by the airfoil may depend on speed of airflow, density of air, total area of an airfoil and/or segment thereof, and/or an angle of attack between air and the airfoil. For example, and without limitation, electric aircraft 200 are designed to be as lightweight as possible. Reducing the weight of the aircraft and designing to reduce the number of components is essential to optimize the weight. To save energy, it may be useful to reduce weight of components of electric aircraft 200, including without limitation propulsors and/or propulsion assemblies. In an embodiment, motor 224 may eliminate need for many external structural features that otherwise might be needed to join one component to another component. Motor 224 may also increase energy efficiency by enabling a lower physical propulsor profile, reducing drag and/or wind resistance. This may also increase durability by lessening the extent to which drag and/or wind resistance add to forces acting on electric aircraft 200 and/or propulsors.

With continued reference to FIG. 1 , system 100 may include a battery management system consistent with any battery management system as described in U.S. patent application Ser. No. 17/108,798, filed on Dec. 1, 2020, and titled, “SYSTEMS AND METHODS FOR BATTERY MANAGEMENT SYSTEM INTEGRATED IN A BATTERY PACK CONFIGURED FOR USE IN AN ELECTRIC AIRCRAFT”, the entirety of which is incorporated herein by reference.

Referring now to FIG. 3 , an embodiment of sensor suite 300 is presented. The herein disclosed system and method may comprise a plurality of sensors in the form of individual sensors or a sensor suite working in tandem or individually. A sensor suite may include a plurality of independent sensors, as described herein, where any number of the described sensors may be used to detect any number of physical or electrical quantities associated with an aircraft power system or an electrical energy storage system. Independent sensors may include separate sensors measuring physical or electrical quantities that may be powered by and/or in communication with circuits independently, where each may signal sensor output to a control circuit such as a user graphical interface. In a non-limiting example, there may be four independent sensors housed in and/or on battery pack measuring temperature, electrical characteristic such as voltage, amperage, resistance, or impedance, or any other parameters and/or quantities as described in this disclosure. In an embodiment, use of a plurality of independent sensors may result in redundancy configured to employ more than one sensor that measures the same phenomenon, those sensors being of the same type, a combination of, or another type of sensor not disclosed, so that in the event one sensor fails, the ability of a battery management system and/or user to detect phenomenon is maintained and in a non-limiting example, a user alter aircraft usage pursuant to sensor readings.

Sensor suite 300 includes a moisture sensor 304. “Moisture,” as used in this disclosure, is the presence of water, this may include vaporized water in air, condensation on the surfaces of objects, or concentrations of liquid water. Moisture may include humidity. “Humidity,” as used in this disclosure, is the property of a gaseous medium (almost always air) to hold water in the form of vapor. An amount of water vapor contained within a parcel of air can vary significantly. Water vapor is generally invisible to the human eye and may be damaging to electrical components. There are three primary measurements of humidity, absolute, relative, specific humidity. “Absolute humidity,” for the purposes of this disclosure, describes the water content of air and is expressed in either grams per cubic meters or grams per kilogram. “Relative humidity,” for the purposes of this disclosure, is expressed as a percentage, indicating a present stat of absolute humidity relative to a maximum humidity given the same temperature. “Specific humidity,” for the purposes of this disclosure, is the ratio of water vapor mass to total moist air parcel mass, where parcel is a given portion of a gaseous medium. Moisture sensor 304 may be psychrometer. Moisture sensor 304 may be a hygrometer. Moisture sensor 304 may be configured to act as or include a humidistat. A “humidistat,” for the purposes of this disclosure, is a humidity-triggered switch, often used to control another electronic device. Moisture sensor 304 may use capacitance to measure relative humidity and include in itself, or as an external component, include a device to convert relative humidity measurements to absolute humidity measurements. “Capacitance,” for the purposes of this disclosure, is the ability of a system to store an electric charge, in this case the system is a parcel of air which may be near, adjacent to, or above a battery cell.

With continued reference to FIG. 3 , sensor suite 300 may include electrical sensors 308. Electrical sensors 308 may be configured to measure voltage across a component, electrical current through a component, and resistance of a component. Electrical sensors 308 may include separate sensors to measure each of the previously disclosed electrical characteristics such as voltmeter, ammeter, and ohmmeter, respectively.

Alternatively or additionally, and with continued reference to FIG. 3 , sensor suite 300 include a sensor or plurality thereof that may detect voltage and direct the charging of individual battery cells according to charge level; detection may be performed using any suitable component, set of components, and/or mechanism for direct or indirect measurement and/or detection of voltage levels, including without limitation comparators, analog to digital converters, any form of voltmeter, or the like. Sensor suite 300 and/or a control circuit incorporated therein and/or communicatively connected thereto may be configured to adjust charge to one or more battery cells as a function of a charge level and/or a detected parameter. For instance, and without limitation, sensor suite 300 may be configured to determine that a charge level of a battery cell is high based on a detected voltage level of that battery cell or portion of the battery pack. Sensor suite 300 may alternatively or additionally detect a charge reduction event, defined for purposes of this disclosure as any temporary or permanent state of a battery cell requiring reduction or cessation of charging; a charge reduction event may include a cell being fully charged and/or a cell undergoing a physical and/or electrical process that makes continued charging at a current voltage and/or current level inadvisable due to a risk that the cell will be damaged, will overheat, or the like. Detection of a charge reduction event may include detection of a temperature, of the cell above a threshold level, detection of a voltage and/or resistance level above or below a threshold, or the like. Sensor suite 300 may include digital sensors, analog sensors, or a combination thereof. Sensor suite 300 may include digital-to-analog converters (DAC), analog-to-digital converters (ADC, A/D, A-to-D), a combination thereof, or other signal conditioning components used in transmission of a first plurality of battery pack data to a destination over wireless or wired connection.

With continued reference to FIG. 3 , sensor suite 300 may include thermocouples, thermistors, thermometers, passive infrared sensors, resistance temperature sensors (RTD's), semiconductor based integrated circuits (IC), a combination thereof or another undisclosed sensor type, alone or in combination. Temperature, for the purposes of this disclosure, and as would be appreciated by someone of ordinary skill in the art, is a measure of the heat energy of a system. Temperature, as measured by any number or combinations of sensors present within sensor suite 300, may be measured in Fahrenheit (° F.), Celsius (° C.), Kelvin (° K), or another scale alone or in combination. The temperature measured by sensors may comprise electrical signals which are transmitted to their appropriate destination wireless or through a wired connection.

With continued reference to FIG. 3 , sensor suite 300 may include a sensor configured to detect gas that may be emitted during or after a cell failure. “Cell failure,” for the purposes of this disclosure, refers to a malfunction of a battery cell, which may be an electrochemical cell, which renders the cell inoperable for its designed function, namely providing electrical energy to at least a portion of an electric aircraft. Byproducts of cell failure 312 may include gaseous discharge including oxygen, hydrogen, carbon dioxide, methane, carbon monoxide, a combination thereof, or another undisclosed gas, alone or in combination. Further the sensor configured to detect vent gas from electrochemical cells may comprise a gas detector. For the purposes of this disclosure, a “gas detector” is a device used to detect a gas is present in an area. Gas detectors, and more specifically, the gas sensor that may be used in sensor suite 300, may be configured to detect combustible, flammable, toxic, oxygen depleted, a combination thereof, or another type of gas alone or in combination. The gas sensor that may be present in sensor suite 300 may include a combustible gas, photoionization detectors, electrochemical gas sensors, ultrasonic sensors, metal-oxide-semiconductor (MOS) sensors, infrared imaging sensors, a combination thereof, or another undisclosed type of gas sensor alone or in combination. Sensor suite 300 may include sensors that are configured to detect non-gaseous byproducts of cell failure 312 including, in non-limiting examples, liquid chemical leaks including aqueous alkaline solution, ionomer, molten phosphoric acid, liquid electrolytes with redox shuttle and ionomer, and salt water, among others. Sensor suite 300 may include sensors that are configured to detect non-gaseous byproducts of cell failure 312 including, in non-limiting examples, electrical anomalies as detected by any of the previous disclosed sensors or components.

With continued reference to FIG. 3 , sensor suite 300 may be configured to detect events where voltage nears an upper voltage threshold or lower voltage threshold. The upper voltage threshold may be stored in data storage system for comparison with an instant measurement taken by any combination of sensors present within sensor suite 300. The upper voltage threshold may be calculated and calibrated based on factors relating to battery cell health, maintenance history, location within battery pack, designed application, and type, among others. Sensor suite 300 may measure voltage at an instant, over a period of time, or periodically. Sensor suite 300 may be configured to operate at any of these detection modes, switch between modes, or simultaneous measure in more than one mode. A first battery management component may detect through sensor suite 300 events where voltage nears the lower voltage threshold. The lower voltage threshold may indicate power loss to or from an individual battery cell or portion of the battery pack. A first battery management component may detect through sensor suite 300 events where voltage exceeds the upper and lower voltage threshold. Events where voltage exceeds the upper and lower voltage threshold may indicate battery cell failure or electrical anomalies that could lead to potentially dangerous situations for aircraft and personnel that may be present in or near its operation.

Referring now to FIG. 4 , an exemplary method 400 of manufacturing a battery module casing for use in an electric vehicle is presented in flow diagram form. At step 405, method includes receiving at least a battery cell 104. The at least a battery cell 104 may be consistent with any battery cell as described herein. The at least a battery cell 104 includes at least a pair of cell tabs 108. At least a pair of cell tabs 108 may be consistent with any pair of cell tabs as described herein. At least a battery cell 104 includes at least a conductor connecting to it. At least a conductor may be consistent with any conductor described herein

With continued reference to FIG. 4 , at step 410, method includes receiving at least a battery module casing. Casing includes at least a lithiophobic surface containing an ejecta barrier. At least a lithiophobic surface may be consistent with any lithiophobic surface as described herein. Ejecta barrier may be consistent with any ejecta barrier as described herein.

With continued reference to FIG. 4 , at step 415, method includes configuring at least a battery cell 104 to power an electric aircraft such as aircraft 200. At least a battery cell 104 may be configured to be wired to one or more other battery cells consistent with this disclosure in order to power one or more electric aircraft. At least a battery cell 104 may include at least a pair of cell tabs 108 that are electrically connected to a bus bar. At least a pair of cell tabs 108 may be consistent with any cell tabs are described herein. The bus bar may be consistent with any bus bars are described herein.

Referring now to FIG. 5 , an exemplary embodiment of a machine-learning module 500 that may perform one or more machine-learning processes as described in this disclosure is illustrated. Machine-learning module may perform determinations, classification, and/or analysis steps, methods, processes, or the like as described in this disclosure using machine learning processes. A “machine learning process,” as used in this disclosure, is a process that automatedly uses training data 504 to generate an algorithm that will be performed by a computing device/module to produce outputs 508 given data provided as inputs 512; this is in contrast to a non-machine learning software program where the commands to be executed are determined in advance by a user and written in a programming language.

Still referring to FIG. 5 , “training data,” as used herein, is data containing correlations that a machine-learning process may use to model relationships between two or more categories of data elements. For instance, and without limitation, training data 504 may include a plurality of data entries, each entry representing a set of data elements that were recorded, received, and/or generated together; data elements may be correlated by shared existence in a given data entry, by proximity in a given data entry, or the like. Multiple data entries in training data 504 may evince one or more trends in correlations between categories of data elements; for instance, and without limitation, a higher value of a first data element belonging to a first category of data element may tend to correlate to a higher value of a second data element belonging to a second category of data element, indicating a possible proportional or other mathematical relationship linking values belonging to the two categories. Multiple categories of data elements may be related in training data 504 according to various correlations; correlations may indicate causative and/or predictive links between categories of data elements, which may be modeled as relationships such as mathematical relationships by machine-learning processes as described in further detail below. Training data 504 may be formatted and/or organized by categories of data elements, for instance by associating data elements with one or more descriptors corresponding to categories of data elements. As a non-limiting example, training data 504 may include data entered in standardized forms by persons or processes, such that entry of a given data element in a given field in a form may be mapped to one or more descriptors of categories. Elements in training data 504 may be linked to descriptors of categories by tags, tokens, or other data elements; for instance, and without limitation, training data 504 may be provided in fixed-length formats, formats linking positions of data to categories such as comma-separated value (CSV) formats and/or self-describing formats such as extensible markup language (XML), JavaScript Object Notation (JSON), or the like, enabling processes or devices to detect categories of data.

Alternatively or additionally, and continuing to refer to FIG. 5 , training data 504 may include one or more elements that are not categorized; that is, training data 504 may not be formatted or contain descriptors for some elements of data. Machine-learning algorithms and/or other processes may sort training data 504 according to one or more categorizations using, for instance, natural language processing algorithms, tokenization, detection of correlated values in raw data and the like; categories may be generated using correlation and/or other processing algorithms. As a non-limiting example, in a corpus of text, phrases making up a number “n” of compound words, such as nouns modified by other nouns, may be identified according to a statistically significant prevalence of n-grams containing such words in a particular order; such an n-gram may be categorized as an element of language such as a “word” to be tracked similarly to single words, generating a new category as a result of statistical analysis. Similarly, in a data entry including some textual data, a person's name may be identified by reference to a list, dictionary, or other compendium of terms, permitting ad-hoc categorization by machine-learning algorithms, and/or automated association of data in the data entry with descriptors or into a given format. The ability to categorize data entries automatedly may enable the same training data 504 to be made applicable for two or more distinct machine-learning algorithms as described in further detail below. Training data 504 used by machine-learning module 500 may correlate any input data as described in this disclosure to any output data as described in this disclosure. As a non-limiting illustrative example flight elements and/or pilot signals may be inputs, wherein an output may be an autonomous function.

Further referring to FIG. 5 , training data may be filtered, sorted, and/or selected using one or more supervised and/or unsupervised machine-learning processes and/or models as described in further detail below; such models may include without limitation a training data classifier 516. Training data classifier 516 may include a “classifier,” which as used in this disclosure is a machine-learning model as defined below, such as a mathematical model, neural net, or program generated by a machine learning algorithm known as a “classification algorithm,” as described in further detail below, that sorts inputs into categories or bins of data, outputting the categories or bins of data and/or labels associated therewith. A classifier may be configured to output at least a datum that labels or otherwise identifies a set of data that are clustered together, found to be close under a distance metric as described below, or the like. Machine-learning module 500 may generate a classifier using a classification algorithm, defined as a processes whereby a computing device and/or any module and/or component operating thereon derives a classifier from training data 504. Classification may be performed using, without limitation, linear classifiers such as without limitation logistic regression and/or naive Bayes classifiers, nearest neighbor classifiers such as k-nearest neighbors classifiers, support vector machines, least squares support vector machines, fisher's linear discriminant, quadratic classifiers, decision trees, boosted trees, random forest classifiers, learning vector quantization, and/or neural network-based classifiers. As a non-limiting example, training data classifier may classify elements of training data to sub-categories of flight elements such as torques, forces, thrusts, directions, and the like thereof.

Still referring to FIG. 5 , machine-learning module 500 may be configured to perform a lazy-learning process 520 and/or protocol, which may alternatively be referred to as a “lazy loading” or “call-when-needed” process and/or protocol, may be a process whereby machine learning is conducted upon receipt of an input to be converted to an output, by combining the input and training set to derive the algorithm to be used to produce the output on demand. For instance, an initial set of simulations may be performed to cover an initial heuristic and/or “first guess” at an output and/or relationship. As a non-limiting example, an initial heuristic may include a ranking of associations between inputs and elements of training data 504. Heuristic may include selecting some number of highest-ranking associations and/or training data 504 elements. Lazy learning may implement any suitable lazy learning algorithm, including without limitation a K-nearest neighbors algorithm, a lazy naïve Bayes algorithm, or the like; persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various lazy-learning algorithms that may be applied to generate outputs as described in this disclosure, including without limitation lazy learning applications of machine-learning algorithms as described in further detail below.

Alternatively or additionally, and with continued reference to FIG. 5 , machine-learning processes as described in this disclosure may be used to generate machine-learning models 524. A “machine-learning model,” as used in this disclosure, is a mathematical and/or algorithmic representation of a relationship between inputs and outputs, as generated using any machine-learning process including without limitation any process as described above, and stored in memory; an input is submitted to a machine-learning model 524 once created, which generates an output based on the relationship that was derived. For instance, and without limitation, a linear regression model, generated using a linear regression algorithm, may compute a linear combination of input data using coefficients derived during machine-learning processes to calculate an output datum. As a further non-limiting example, a machine-learning model 524 may be generated by creating an artificial neural network, such as a convolutional neural network comprising an input layer of nodes, one or more intermediate layers, and an output layer of nodes. Connections between nodes may be created via the process of “training” the network, in which elements from a training data 504 set are applied to the input nodes, a suitable training algorithm (such as Levenberg-Marquardt, conjugate gradient, simulated annealing, or other algorithms) is then used to adjust the connections and weights between nodes in adjacent layers of the neural network to produce the desired values at the output nodes. This process is sometimes referred to as deep learning.

Still referring to FIG. 5 , machine-learning algorithms may include at least a supervised machine-learning process 528. At least a supervised machine-learning process 528, as defined herein, include algorithms that receive a training set relating a number of inputs to a number of outputs, and seek to find one or more mathematical relations relating inputs to outputs, where each of the one or more mathematical relations is optimal according to some criterion specified to the algorithm using some scoring function. For instance, a supervised learning algorithm may include flight elements and/or pilot signals as described above as inputs, autonomous functions as outputs, and a scoring function representing a desired form of relationship to be detected between inputs and outputs; scoring function may, for instance, seek to maximize the probability that a given input and/or combination of elements inputs is associated with a given output to minimize the probability that a given input is not associated with a given output. Scoring function may be expressed as a risk function representing an “expected loss” of an algorithm relating inputs to outputs, where loss is computed as an error function representing a degree to which a prediction generated by the relation is incorrect when compared to a given input-output pair provided in training data 504. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various possible variations of at least a supervised machine-learning process 528 that may be used to determine relation between inputs and outputs. Supervised machine-learning processes may include classification algorithms as defined above.

Further referring to FIG. 5 , machine learning processes may include at least an unsupervised machine-learning processes 532. An unsupervised machine-learning process, as used herein, is a process that derives inferences in datasets without regard to labels; as a result, an unsupervised machine-learning process may be free to discover any structure, relationship, and/or correlation provided in the data. Unsupervised processes may not require a response variable; unsupervised processes may be used to find interesting patterns and/or inferences between variables, to determine a degree of correlation between two or more variables, or the like.

Still referring to FIG. 5 , machine-learning module 500 may be designed and configured to create a machine-learning model 524 using techniques for development of linear regression models. Linear regression models may include ordinary least squares regression, which aims to minimize the square of the difference between predicted outcomes and actual outcomes according to an appropriate norm for measuring such a difference (e.g. a vector-space distance norm); coefficients of the resulting linear equation may be modified to improve minimization. Linear regression models may include ridge regression methods, where the function to be minimized includes the least-squares function plus term multiplying the square of each coefficient by a scalar amount to penalize large coefficients. Linear regression models may include least absolute shrinkage and selection operator (LASSO) models, in which ridge regression is combined with multiplying the least-squares term by a factor of 1 divided by double the number of samples. Linear regression models may include a multi-task lasso model wherein the norm applied in the least-squares term of the lasso model is the Frobenius norm amounting to the square root of the sum of squares of all terms. Linear regression models may include the elastic net model, a multi-task elastic net model, a least angle regression model, a LARS lasso model, an orthogonal matching pursuit model, a Bayesian regression model, a logistic regression model, a stochastic gradient descent model, a perceptron model, a passive aggressive algorithm, a robustness regression model, a Huber regression model, or any other suitable model that may occur to persons skilled in the art upon reviewing the entirety of this disclosure. Linear regression models may be generalized in an embodiment to polynomial regression models, whereby a polynomial equation (e.g. a quadratic, cubic or higher-order equation) providing a best predicted output/actual output fit is sought; similar methods to those described above may be applied to minimize error functions, as will be apparent to persons skilled in the art upon reviewing the entirety of this disclosure.

Continuing to refer to FIG. 5 , machine-learning algorithms may include, without limitation, linear discriminant analysis. Machine-learning algorithm may include quadratic discriminate analysis. Machine-learning algorithms may include kernel ridge regression. Machine-learning algorithms may include support vector machines, including without limitation support vector classification-based regression processes. Machine-learning algorithms may include stochastic gradient descent algorithms, including classification and regression algorithms based on stochastic gradient descent. Machine-learning algorithms may include nearest neighbors algorithms. Machine-learning algorithms may include Gaussian processes such as Gaussian Process Regression. Machine-learning algorithms may include cross-decomposition algorithms, including partial least squares and/or canonical correlation analysis. Machine-learning algorithms may include naïve Bayes methods. Machine-learning algorithms may include algorithms based on decision trees, such as decision tree classification or regression algorithms. Machine-learning algorithms may include ensemble methods such as bagging meta-estimator, forest of randomized tress, AdaBoost, gradient tree boosting, and/or voting classifier methods. Machine-learning algorithms may include neural net algorithms, including convolutional neural net processes.

The foregoing has been a detailed description of illustrative embodiments of the invention. Various modifications and additions can be made without departing from the spirit and scope of this invention. Features of each of the various embodiments described above may be combined with features of other described embodiments as appropriate in order to provide a multiplicity of feature combinations in associated new embodiments. Furthermore, while the foregoing describes a number of separate embodiments, what has been described herein is merely illustrative of the application of the principles of the present invention. Additionally, although particular methods herein may be illustrated and/or described as being performed in a specific order, the ordering is highly variable within ordinary skill to achieve embodiments according to this disclosure. Accordingly, this description is meant to be taken only by way of example, and not to otherwise limit the scope of this invention.

It is to be noted that any one or more of the aspects and embodiments described herein may be conveniently implemented using one or more machines (e.g., one or more computing devices that are utilized as a user computing device for an electronic document, one or more server devices, such as a document server, etc.) programmed according to the teachings of the present specification, as will be apparent to those of ordinary skill in the computer art. Appropriate software coding can readily be prepared by skilled programmers based on the teachings of the present disclosure, as will be apparent to those of ordinary skill in the software art. Aspects and implementations discussed above employing software and/or software modules may also include appropriate hardware for assisting in the implementation of the machine executable instructions of the software and/or software module.

Such software may be a computer program product that employs a machine-readable storage medium. A machine-readable storage medium may be any medium that is capable of storing and/or encoding a sequence of instructions for execution by a machine (e.g., a computing device) and that causes the machine to perform any one of the methodologies and/or embodiments described herein. Examples of a machine-readable storage medium include, but are not limited to, a magnetic disk, an optical disc (e.g., CD, CD-R, DVD, DVD-R, etc.), a magneto-optical disk, a read-only memory “ROM” device, a random-access memory “RAM” device, a magnetic card, an optical card, a solid-state memory device, an EPROM, an EEPROM, and any combinations thereof. A machine-readable medium, as used herein, is intended to include a single medium as well as a collection of physically separate media, such as, for example, a collection of compact discs or one or more hard disk drives in combination with a computer memory. As used herein, a machine-readable storage medium does not include transitory forms of signal transmission.

Such software may also include information (e.g., data) carried as a data signal on a data carrier, such as a carrier wave. For example, machine-executable information may be included as a data-carrying signal embodied in a data carrier in which the signal encodes a sequence of instruction, or portion thereof, for execution by a machine (e.g., a computing device) and any related information (e.g., data structures and data) that causes the machine to perform any one of the methodologies and/or embodiments described herein.

Examples of a computing device include, but are not limited to, an electronic book reading device, a computer workstation, a terminal computer, a server computer, a handheld device (e.g., a tablet computer, a smartphone, etc.), a web appliance, a network router, a network switch, a network bridge, any machine capable of executing a sequence of instructions that specify an action to be taken by that machine, and any combinations thereof. In one example, a computing device may include and/or be included in a kiosk.

FIG. 6 shows a diagrammatic representation of one embodiment of a computing device in the exemplary form of a computer system 600 within which a set of instructions for causing a control system to perform any one or more of the aspects and/or methodologies of the present disclosure may be executed. It is also contemplated that multiple computing devices may be utilized to implement a specially configured set of instructions for causing one or more of the devices to perform any one or more of the aspects and/or methodologies of the present disclosure. Computer system 600 includes a processor 604 and a memory 608 that communicate with each other, and with other components, via a bus 612. Bus 612 may include any of several types of bus structures including, but not limited to, a memory bus, a memory controller, a peripheral bus, a local bus, and any combinations thereof, using any of a variety of bus architectures.

Processor 604 may include any suitable processor, such as without limitation a processor incorporating logical circuitry for performing arithmetic and logical operations, such as an arithmetic and logic unit (ALU), which may be regulated with a state machine and directed by operational inputs from memory and/or sensors; processor 604 may be organized according to Von Neumann and/or Harvard architecture as a non-limiting example. Processor 604 may include, incorporate, and/or be incorporated in, without limitation, a microcontroller, microprocessor, digital signal processor (DSP), Field Programmable Gate Array (FPGA), Complex Programmable Logic Device (CPLD), Graphical Processing Unit (GPU), general purpose GPU, Tensor Processing Unit (TPU), analog or mixed signal processor, Trusted Platform Module (TPM), a floating-point unit (FPU), and/or system on a chip (SoC).

Memory 608 may include various components (e.g., machine-readable media) including, but not limited to, a random-access memory component, a read only component, and any combinations thereof. In one example, a basic input/output system 616 (BIOS), including basic routines that help to transfer information between elements within computer system 600, such as during start-up, may be stored in memory 608. Memory 608 may also include (e.g., stored on one or more machine-readable media) instructions (e.g., software) 620 embodying any one or more of the aspects and/or methodologies of the present disclosure. In another example, memory 608 may further include any number of program modules including, but not limited to, an operating system, one or more application programs, other program modules, program data, and any combinations thereof.

Computer system 600 may also include a storage device 624. Examples of a storage device (e.g., storage device 624) include, but are not limited to, a hard disk drive, a magnetic disk drive, an optical disc drive in combination with an optical medium, a solid-state memory device, and any combinations thereof. Storage device 624 may be connected to bus 612 by an appropriate interface (not shown). Example interfaces include, but are not limited to, SCSI, advanced technology attachment (ATA), serial ATA, universal serial bus (USB), IEEE 1394 (FIREWIRE), and any combinations thereof. In one example, storage device 624 (or one or more components thereof) may be removably interfaced with computer system 600 (e.g., via an external port connector (not shown)). Particularly, storage device 624 and an associated machine-readable medium 628 may provide nonvolatile and/or volatile storage of machine-readable instructions, data structures, program modules, and/or other data for computer system 600. In one example, software 620 may reside, completely or partially, within machine-readable medium 628. In another example, software 620 may reside, completely or partially, within processor 604.

Computer system 600 may also include an input device 632. In one example, a user of computer system 600 may enter commands and/or other information into computer system 600 via input device 632. Examples of an input device 632 include, but are not limited to, an alpha-numeric input device (e.g., a keyboard), a pointing device, a joystick, a gamepad, an audio input device (e.g., a microphone, a voice response system, etc.), a cursor control device (e.g., a mouse), a touchpad, an optical scanner, a video capture device (e.g., a still camera, a video camera), a touchscreen, and any combinations thereof. Input device 632 may be interfaced to bus 612 via any of a variety of interfaces (not shown) including, but not limited to, a serial interface, a parallel interface, a game port, a USB interface, a FIREWIRE interface, a direct interface to bus 612, and any combinations thereof. Input device 632 may include a touch screen interface that may be a part of or separate from display 636, discussed further below. Input device 632 may be utilized as a user selection device for selecting one or more graphical representations in a graphical interface as described above.

A user may also input commands and/or other information to computer system 600 via storage device 624 (e.g., a removable disk drive, a flash drive, etc.) and/or network interface device 640. A network interface device, such as network interface device 640, may be utilized for connecting computer system 600 to one or more of a variety of networks, such as network 644, and one or more remote devices 648 connected thereto. Examples of a network interface device include, but are not limited to, a network interface card (e.g., a mobile network interface card, a LAN card), a modem, and any combination thereof. Examples of a network include, but are not limited to, a wide area network (e.g., the Internet, an enterprise network), a local area network (e.g., a network associated with an office, a building, a campus or other relatively small geographic space), a telephone network, a data network associated with a telephone/voice provider (e.g., a mobile communications provider data and/or voice network), a direct connection between two computing devices, and any combinations thereof. A network, such as network 644, may employ a wired and/or a wireless mode of communication. In general, any network topology may be used. Information (e.g., data, software 620, etc.) may be communicated to and/or from computer system 600 via network interface device 640.

Computer system 600 may further include a video display adapter 652 for communicating a displayable image to a display device, such as display device 636. Examples of a display device include, but are not limited to, a liquid crystal display (LCD), a cathode ray tube (CRT), a plasma display, a light emitting diode (LED) display, and any combinations thereof. Display adapter 652 and display device 636 may be utilized in combination with processor 604 to provide graphical representations of aspects of the present disclosure. In addition to a display device, computer system 600 may include one or more other peripheral output devices including, but not limited to, an audio speaker, a printer, and any combinations thereof. Such peripheral output devices may be connected to bus 612 via a peripheral interface 656. Examples of a peripheral interface include, but are not limited to, a serial port, a USB connection, a FIREWIRE connection, a parallel connection, and any combinations thereof.

The foregoing has been a detailed description of illustrative embodiments of the invention. Various modifications and additions can be made without departing from the spirit and scope of this invention. Features of each of the various embodiments described above may be combined with features of other described embodiments as appropriate in order to provide a multiplicity of feature combinations in associated new embodiments. Furthermore, while the foregoing describes a number of separate embodiments, what has been described herein is merely illustrative of the application of the principles of the present invention. Additionally, although particular methods herein may be illustrated and/or described as being performed in a specific order, the ordering is highly variable within ordinary skill to achieve methods, systems, and software according to the present disclosure. Accordingly, this description is meant to be taken only by way of example, and not to otherwise limit the scope of this invention.

Exemplary embodiments have been disclosed above and illustrated in the accompanying drawings. It will be understood by those skilled in the art that various changes, omissions and additions may be made to that which is specifically disclosed herein without departing from the spirit and scope of the present invention. 

What is claimed is:
 1. A battery module configured for use in an electric aircraft, the battery module comprising: a battery cell, the battery cell comprising: a pair of cell tabs; and a conductor connected to an electric bus comprising a ring bus, wherein the electric bus is configured to allow cooling of the conductor; a battery module casing, the battery module casing configured to encompass the battery cell and the conductor, wherein the battery module casing comprises: a lithiophobic surface including an ejecta barrier, wherein the lithiophobic surface is disposed on an exterior face of the battery module casing, and wherein the exterior face comprises an opening; and a non-lithiophobic surface, wherein the non-lithiophobic surface is configured to vent cell ejecta along a flow path comprising a check valve providing for a unidirectional flow path, and wherein the battery module is configured to power the electric aircraft.
 2. The battery module of claim 1, wherein the electric aircraft comprises an electric vertical takeoff and landing aircraft.
 3. The battery module of claim 1, wherein the battery module comprises a sensor suite.
 4. The battery module of claim 1, wherein the at least a battery cell comprises a plurality of conductive tabs welded to the conductor.
 5. The battery module of claim 1, wherein the battery cell is connected to the battery module casing by a bonding.
 6. The battery module of claim 1, wherein the battery module casing is configured to closely match dimensions of the battery cell.
 7. The battery module of claim 1, wherein the lithiophobic surface is configured to prevent ejecta from traveling outside the battery module casing.
 8. The battery module of claim 1, wherein the lithiophobic surface is configured to transfer heat from the battery cell to the battery module casing.
 9. A method of manufacturing a battery cell casing for use in an electric aircraft, the method comprising: receiving a battery cell, the battery cell comprising: a pair of cell tabs; a conductor, wherein the conductor is connected to an electric bus comprising a ring bus, and wherein the electric bus is configured to allow cooling of the conductor; receiving the battery module casing, the battery module casing comprising: a lithiophobic surface containing an ejecta barrier, wherein the lithiophobic surface is disposed on an exterior face of the battery module casing, and wherein the exterior face comprises an opening; a non-lithiophobic surface configured to vent cell ejecta along a flow path comprising a check valve providing for a unidirectional flow path; placing the battery cell into the battery module casing; and configuring the battery cell to power the electric aircraft.
 10. The method of claim 9, wherein the electric aircraft comprises an electric vertical takeoff and landing aircraft.
 11. The method of claim 9, wherein the battery module comprises a sensor suite.
 12. The method of claim 9, wherein the battery cell comprises a plurality of conductive tabs welded to the conductor.
 13. The method of claim 9, wherein the battery cell is connected to the battery module casing by a bonding.
 14. The method of claim 9, wherein the battery module casing is configured to closely match dimensions of the battery cell.
 15. The method of claim 9, wherein the lithiophobic surface is configured to prevent ejecta from traveling outside the battery module casing.
 16. The method of claim 9, wherein the lithiophobic surface is configured to transfer heat from the battery cell to the battery module casing. 